CN102308401B - Thermoelectric generation for a gas turbine - Google Patents

Thermoelectric generation for a gas turbine Download PDF

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Publication number
CN102308401B
CN102308401B CN201080006889.4A CN201080006889A CN102308401B CN 102308401 B CN102308401 B CN 102308401B CN 201080006889 A CN201080006889 A CN 201080006889A CN 102308401 B CN102308401 B CN 102308401B
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CN
China
Prior art keywords
annular region
electric power
cold fluid
turbine
wall
Prior art date
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Application number
CN201080006889.4A
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Chinese (zh)
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CN102308401A (en
Inventor
克里斯托夫·布瑞礼
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Helicopter Engines SAS
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Turbomeca SA
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Publication of CN102308401A publication Critical patent/CN102308401A/en
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Classifications

    • H—ELECTRICITY
    • H10—SEMICONDUCTOR DEVICES; ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N—ELECTRIC SOLID-STATE DEVICES NOT OTHERWISE PROVIDED FOR
    • H10N10/00—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects
    • H10N10/10—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects
    • H10N10/13—Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the heat-exchanging means at the junction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fuel Cell (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

The invention relates to a device for generating electric power in a gas turbine or the like of an aircraft, including a plurality of thermoelectric cells (44) having a surface surrounding a heat source (SC). The invention is characterized in that the cold source (SF) consists of the circulation of a cold fluid (F) carried out on the other surface of said thermoelectric cells.

Description

The thermoelectricity of gas turbine generates
The present invention relates to the device for aircraft gas turbines or analog generation electric power.
The electric weight of interior of aircraft devices consume is very important.This electric power is produced by alternating current generator conventionally, and this alternating current generator obtains mechanical energy from gas turbine.Therefore, can not increase the device of the fuel consumption of aircraft in electric power be useful producing.
In addition, well-known, thermoelectric cell can produce electric power under the action of thermal difference that it is applied.
Accompanying drawing 1 shows such thermoelectric cell 10.It is made up of semiconductor junction substantially, and this semiconductor interface is made up of two elements 12 and 14 that are doped to respectively N-type and P type.Above-mentioned two elements link together by electric conductor 16, and have respectively the electrical connection that forms terminal 18 and 19.Conventionally, said modules forms a unit thermoelectric cell, is arranged on such as between strutting piece 20 and 22 such two electric insulation strutting pieces, and this strutting piece helps battery to be fixed on other parts.Certainly multiple independent batteries gang mutually.
In addition, well-known is that the temperature difference existing between the efficiency of above-mentioned battery or two surfaces of output and battery is directly directly proportional, and for example, described surface can be made up of insulated support 20 and 22.
PCT patent application WO 2005/017331 has described a kind of thermoelectric generator for gas-turbine unit, and this gas-turbine unit is specifically for advancing aircraft.
Above-mentioned patent application has proposed to install the thermoelectric cell group of ring-type around hot-zone, but does not describe the mounting condition of above-mentioned thermoelectric cell group in detail.
Unfortunately, just as mentioning above, the efficiency of this generating equipment directly depends on the temperature difference between thermal source and low-temperature receiver, and thermoelectric cell is just arranged between described thermal source and low-temperature receiver.
An object of the present invention is to provide a kind of device for aircraft gas turbines or analog generation electric power, this device significantly improves the efficiency of thermoelectric cell, and the fuel consumption of not obvious increase aircraft.
For realizing this object, the above-mentioned device for aircraft gas turbines or analog generation electric power comprises multiple thermoelectric cells, a surface of these thermoelectric cells is around thermal source, and is characterised in that low-temperature receiver is made up of mobile cold fluid on another surface of described thermoelectric cell.
Be understandable that, in the present embodiment, the low-temperature receiver that is applied to thermoelectric cell is made up of cold fluid flow, has improved thus the energy efficiency of thermoelectric cell.
In preferred the first execution mode, electrical power generation system is characterised in that described cold fluid is selected from following group: for the fuel of turbine; Cold oil or lubricating oil; From the air of the compressor of turbine; The air of cooling engine room; And the air of turbine outside.
Be understandable that, use the above fluid of enumerating, particularly use cold oil or fuel can bring higher cooling capacity, and substantially can not cause extra fuel consumption, because cold oil or fuel circulate.
In the first embodiment, thermal source is made up of the wall of the nozzle of turbine, and this wall is by waste gas Convective Heating.
In another embodiment, described system is characterised in that described low-temperature receiver is made up of at least one annular region, and cold flow is introduced into this annular region.The inwall of described annular region contacts with the strutting piece of thermoelectric cell.The outer wall of described annular region is shell, cooling by cold fluid convection current.
Preferably, the feature of described device is also that annular region is arranged alternately concentrically, and low-temperature receiver and waste gas alternately flow.Thermoelectric cell is arranged between each annular region.
Be understandable that, be arranged between annular region by these annular regions and by thermoelectric cell, countercurrent heat exchange is provided, greatly improved thus the whole efficiency of power generating device.
More precisely, thermal source wherein has the part annular region of radius helical flow outward of (forming hot fluid) waste gas by least one, and at least one is wherein made up of towards the annular region of inside radius helical flow cold fluid.At least one ring-shaped component being made up of thermoelectric cell is installed concentrically, and a surface of assembly is contacted with cold fluid, and another surface contacts with hot fluid, forms thus cylindrical counterflow heat exchanger.
The present invention also provides the purposes of power generating device of the present invention, and it is for the annex of driven by power gas turbine, such as full powers limit digital electronic controllers (FADEC) or by motor-driven pump.
Finally, the invention provides a kind of helicopter turbogenerator, it comprises power generating device of the present invention.The thermoelectric cell of this device is preferably mounted on the emission nozzle of turbogenerator.
By the description of below the some execution modes that provide as non-limitative example being carried out, the feature and advantage that the present invention may be better understood are provided.
The following drawings is cited in description:
Fig. 1 shows a kind of possible execution mode that is applicable to thermoelectric cell of the present invention;
Fig. 2 is half view that is suitable for the longitudinal section of the aircraft gas turbines that power generating device is installed;
Fig. 3 shows the first execution mode of power generating device;
Fig. 4 shows the first variation execution mode of power generating device;
Fig. 5 A is the perspective view of the nozzle of aircraft gas turbines, and this nozzle is provided with heat exchanger, to improve the whole efficiency of power generating device;
Fig. 5 B is the end-view along the nozzle that heat exchanger is installed of the arrow VB observation in Fig. 5 A;
Fig. 6 is a chart, and showing fuel is how to form low-temperature receiver.
Fig. 2 shows the example that is suitable for the aircraft gas turbines that power generating device of the present invention is installed in a simplified manner.In the figure, can see gas turbine 24, and compressor housing 26, high-pressure turbine housing 28, free turbine housing 30, and outlet nozzle 32.Can also see the axle 34 of the free turbine of gas turbine.
In the execution mode of following power generating device, this device is installed together with the outlet nozzle 32 of gas turbine, or with its gang.Alternatively, device can also be arranged on other thermal part of turbine.
In the first execution mode shown in Fig. 3, power generating device 40 is directly installed on the outer wall 42 of nozzle 32.Preferably, power generating device 40 forms by organizing thermoelectric cell more, and described thermoelectric cell is connected with each other, forms ring-shaped component 44, and these ring-shaped components are uniformly distributed along the length of the wall 42 of nozzle 32.The ring of each annular is made up of the thermoelectric cell of a series of Fig. 1 shown types, electric connection between these thermoelectric cells, and wherein mechanical support 22 and 20 is flexible, on the surface of revolution that can form at the wall 42 by nozzle 32 thus, is combined together.Therefore, the first surface of thermoelectric conversion element 44 contacts by heat bridge with the outer surface of the wall 42 of nozzle 32, and the second surface of thermoelectric conversion element 44 is with the extraneous air contact as low-temperature receiver SF, preferably, form heat bridge by outer wall 48 (interference unit may be installed).As mentioned above, thermal source SC is made up of waste gas G mobile in nozzle 32, and by the inwall 42 of Convective Heating nozzle 32.
Figure 4 illustrates the variation execution mode of power generating device, wherein thermal source SC is still made up of the wall 42 of nozzle 32, but low-temperature receiver SF is made up of cold fluid F mobile in annular space 46, this annular space 46 is by the inwall 48 contacting with the second surface of thermoelectric conversion element 44, and outer wall 50 limits.Obtained so better cold fluid flow, and and thermoelectric cell between better heat exchange because annular space 46 can dispose baffle plate.This execution mode can also use other cold fluids outside deacration, as cold oil or fuel.Even so, also can use extraneous air or the cold air from gas turbine each several part.
Fig. 5 A and 5B show the 3rd execution mode of power generating device.
In above-mentioned figure, can see that the wall 42 of delivery nozzle 32 is as inwall, wall 51 is the outer wall of nozzle 32.Cold fluid F (cold air, cold oil, or fuel) enters by entry conductor 52, and then in concentric annular region 46, (along the direction that is defined as positive direction by convection current) flows, the motion of spinning towards the center of nozzle simultaneously.Packed radial separations part 59 is installed, its guiding cold fluid F screw so that cold fluid F follows suit, this screw is relevant with the conduit 53 that is communicated with annular region 46.An in the end annular region 46 1in (least radius), cold fluid F is discharged to outside by conduit 54.
Hot fluid G (waste gas that nozzle is discharged) takes from by inlet tube conduit 55 waste gas that nozzle is discharged, then in annular region 58, (along the direction that is defined as negative direction by convection current) flows, and starts from exhaust gas region 32 motion of spinning towards the outside of nozzle.Install Packed separator 59 ', its guiding hot fluid G motion so that hot fluid G spins, this screw is relevant with the conduit 56 of connection annular region 58.An in the end annular region 58 1in (maximum radius), hot fluid G turns back in the main waste gas streams of nozzle by conduit 57.
Multiple ring-shaped components that formed by thermoelectric cell 44 are installed in concentric mode, and a surface of each assembly is contacted with cold fluid F, and another surface contacts with hot fluid G.Cylindrical counterflow heat exchanger is so just provided.
Fig. 6 relates to the special circumstances of a kind of cold fluid by fuel composition, has described a kind of possible mode that cold fluid is offered to the annular region 46 (this annular region 46 can be made up of the concentric ring of the equipment described in multiple Fig. 5 B) of the low-temperature receiver that forms power generating device.As shown in Figure 6, fuel tank 60 comprises the low-lift pump 62 that is connected to high-pressure pump 64, and high-pressure pump 64 is transported to fuel adjuster 66 under pressure, and adjuster 66 self is connected to the fuel injector 68 of combustion chamber.Fuel takes out from the outlet of low-lift pump 62 with lower speed, offers the annular region 46 of composition low-temperature receiver.After flowing through annular region 46, fuel re-injects the entrance of low-lift pump 62 by conduit 70.

Claims (7)

1. produce the device of electric power for the gas turbine at aircraft or analog, this device comprises multiple thermoelectric cells (44), a surface of described thermoelectric cell is around thermal source (SC), low-temperature receiver (SF) is made up of cold fluid (F) mobile on another surface of described thermoelectric cell, in described device, the annular region (46) that described low-temperature receiver (SF) is imported to described cold fluid wherein by least one forms, another surface of a wall (48) of described annular region (46) and described thermoelectric cell forms heat bridge, the skin that another wall of described annular region (46) is described device, described device is characterised in that, described thermal source by the part of at least one waste gas therein towards radially outward forming with the mobile annular region of screw (58), described low-temperature receiver by least one cold fluid (F) towards radially inwardly forming with the mobile annular region of screw (46), and at least one ring-shaped component being made up of thermoelectric cell (44) is installed concentrically, a surface of described assembly is contacted with described cold fluid (F), another surface contacts with hot fluid, cylindrical counterflow heat exchanger is provided thus.
2. the device of generation electric power as claimed in claim 1, is characterised in that described cold fluid (F) is selected from following group: for the fuel of described turbine; Cold oil or lubricating oil; Take from the air of the compressor of described turbine; For the air of cooling engine room; And the air of described turbine outside.
3. the device of generation electric power as claimed in claim 1, is characterised in that described thermal source (SC) is made up of the wall (42) of the nozzle (32) of described turbine, and this wall is by waste gas Convective Heating.
4. the device of generation electric power as claimed in claim 2, is characterised in that described thermal source (SC) is made up of the wall (42) of the nozzle (32) of described turbine, and this wall is by waste gas Convective Heating.
5. the device of generation electric power as claimed in claim 1, be characterised in that the annular region (58) that it comprises the connection of multiple mobile parts that have waste gas, the annular region (46) of multiple mobile connections that have described cold fluid, and multiple ring-shaped components that formed (44) by thermoelectric cell, each described ring-shaped component is positioned between the annular region (58) of passing through for waste gas and the annular region (46) of passing through for cold fluid (F).
6. the purposes of the device of the generation electric power as described in claim 1 to 5 any one in the annex of gas turbine as described in driven by power.
7. helicopter turbogenerator, it comprises the device of the generation electric power as described in claim 1 to 5 any one.
CN201080006889.4A 2009-02-06 2010-02-04 Thermoelectric generation for a gas turbine Active CN102308401B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0950739A FR2942077B1 (en) 2009-02-06 2009-02-06 THERMOELECTRIC GENERATION FOR GAS TURBINE
FR0950739 2009-02-06
PCT/FR2010/050176 WO2010089505A1 (en) 2009-02-06 2010-02-04 Thermoelectric generation for a gas turbine

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CN102308401A CN102308401A (en) 2012-01-04
CN102308401B true CN102308401B (en) 2014-07-23

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US (1) US8962968B2 (en)
EP (1) EP2394309B1 (en)
JP (1) JP2012517789A (en)
KR (1) KR101769159B1 (en)
CN (1) CN102308401B (en)
CA (1) CA2751395C (en)
ES (1) ES2418148T3 (en)
FR (1) FR2942077B1 (en)
PL (1) PL2394309T3 (en)
RU (1) RU2534443C2 (en)
WO (1) WO2010089505A1 (en)

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CA2751395C (en) 2018-04-10
FR2942077A1 (en) 2010-08-13
CA2751395A1 (en) 2010-08-12
ES2418148T3 (en) 2013-08-12
CN102308401A (en) 2012-01-04
KR101769159B1 (en) 2017-08-17
KR20110124252A (en) 2011-11-16
WO2010089505A1 (en) 2010-08-12
EP2394309A1 (en) 2011-12-14
RU2011136856A (en) 2013-03-20
US20110283712A1 (en) 2011-11-24
US8962968B2 (en) 2015-02-24
PL2394309T3 (en) 2013-08-30
EP2394309B1 (en) 2013-04-17
FR2942077B1 (en) 2013-08-16
JP2012517789A (en) 2012-08-02
RU2534443C2 (en) 2014-11-27

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